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WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 60-126/1 AIRFOIL (fx601261-il)
Reynolds number: 200,000
Max Cl/Cd: 76.15 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx601261-il-200000-n5.txt
Download as CSV file: xf-fx601261-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 60-126/1 AIRFOIL                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2606   0.08831   0.08505  -0.0449   1.0000   0.0138
  -9.750  -0.2658   0.08444   0.08124  -0.0450   1.0000   0.0136
  -9.250  -0.4084   0.06809   0.06450  -0.0569   1.0000   0.0114
  -9.000  -0.4257   0.06354   0.05998  -0.0582   1.0000   0.0113
  -8.750  -0.4275   0.05846   0.05489  -0.0636   0.9950   0.0112
  -8.500  -0.4265   0.05036   0.04658  -0.0768   0.9754   0.0111
  -8.250  -0.4092   0.04377   0.03971  -0.0898   0.9595   0.0110
  -8.000  -0.3900   0.03849   0.03400  -0.0980   0.9468   0.0108
  -7.750  -0.3643   0.03408   0.02911  -0.1040   0.9373   0.0107
  -7.500  -0.3314   0.03047   0.02501  -0.1091   0.9313   0.0106
  -7.250  -0.3003   0.02779   0.02190  -0.1122   0.9232   0.0107
  -7.000  -0.2644   0.02575   0.01932  -0.1154   0.9171   0.0112
  -6.750  -0.2321   0.02379   0.01711  -0.1176   0.9103   0.0117
  -6.500  -0.1989   0.02225   0.01545  -0.1195   0.9038   0.0121
  -6.250  -0.1652   0.02087   0.01384  -0.1210   0.8972   0.0120
  -6.000  -0.1336   0.01974   0.01254  -0.1220   0.8888   0.0119
  -5.750  -0.1024   0.01875   0.01143  -0.1229   0.8806   0.0118
  -5.500  -0.0725   0.01787   0.01046  -0.1236   0.8718   0.0118
  -5.250  -0.0436   0.01708   0.00961  -0.1240   0.8634   0.0118
  -5.000  -0.0144   0.01637   0.00884  -0.1246   0.8558   0.0118
  -4.750   0.0144   0.01571   0.00811  -0.1251   0.8484   0.0119
  -4.500   0.0434   0.01515   0.00744  -0.1256   0.8407   0.0120
  -4.250   0.0725   0.01466   0.00684  -0.1260   0.8332   0.0121
  -4.000   0.1014   0.01424   0.00630  -0.1263   0.8250   0.0123
  -3.750   0.1303   0.01389   0.00583  -0.1265   0.8167   0.0125
  -3.500   0.1591   0.01359   0.00540  -0.1266   0.8080   0.0129
  -3.250   0.1876   0.01334   0.00504  -0.1267   0.7995   0.0133
  -3.000   0.2165   0.01314   0.00472  -0.1268   0.7920   0.0140
  -2.750   0.2451   0.01293   0.00443  -0.1268   0.7841   0.0151
  -2.500   0.2739   0.01275   0.00415  -0.1268   0.7761   0.0181
  -2.250   0.3036   0.01169   0.00375  -0.1281   0.7674   0.1965
  -2.000   0.3327   0.01117   0.00369  -0.1287   0.7589   0.3317
  -1.750   0.3604   0.01108   0.00378  -0.1286   0.7488   0.3998
  -1.500   0.3886   0.01109   0.00376  -0.1285   0.7396   0.4241
  -1.250   0.4165   0.01111   0.00378  -0.1283   0.7304   0.4480
  -1.000   0.4443   0.01116   0.00383  -0.1281   0.7214   0.4718
  -0.750   0.4723   0.01121   0.00382  -0.1278   0.7119   0.4869
  -0.500   0.4998   0.01122   0.00380  -0.1276   0.7008   0.4954
  -0.250   0.5275   0.01125   0.00377  -0.1274   0.6901   0.5043
   0.000   0.5552   0.01128   0.00376  -0.1271   0.6799   0.5120
   0.250   0.5828   0.01133   0.00376  -0.1269   0.6690   0.5206
   0.500   0.6103   0.01137   0.00380  -0.1267   0.6587   0.5285
   0.750   0.6379   0.01145   0.00381  -0.1264   0.6487   0.5380
   1.000   0.6650   0.01150   0.00387  -0.1261   0.6367   0.5464
   1.250   0.6921   0.01158   0.00392  -0.1258   0.6238   0.5561
   1.500   0.7189   0.01167   0.00398  -0.1255   0.6106   0.5654
   1.750   0.7457   0.01176   0.00405  -0.1251   0.5980   0.5740
   2.000   0.7725   0.01187   0.00414  -0.1248   0.5861   0.5831
   2.250   0.7991   0.01197   0.00426  -0.1244   0.5734   0.5919
   2.500   0.8256   0.01209   0.00437  -0.1240   0.5608   0.6022
   2.750   0.8517   0.01222   0.00450  -0.1236   0.5473   0.6131
   3.000   0.8773   0.01236   0.00463  -0.1231   0.5314   0.6248
   3.250   0.9024   0.01253   0.00479  -0.1224   0.5123   0.6380
   3.500   0.9270   0.01272   0.00494  -0.1217   0.4923   0.6523
   3.750   0.9516   0.01291   0.00512  -0.1210   0.4728   0.6676
   4.000   0.9758   0.01312   0.00534  -0.1203   0.4523   0.6842
   4.250   0.9991   0.01335   0.00556  -0.1194   0.4297   0.7042
   4.500   1.0219   0.01361   0.00579  -0.1184   0.4065   0.7289
   4.750   1.0436   0.01388   0.00606  -0.1172   0.3819   0.7607
   5.000   1.0632   0.01411   0.00633  -0.1155   0.3580   0.8081
   5.250   1.0791   0.01417   0.00649  -0.1129   0.3401   1.0000
   5.500   1.1033   0.01455   0.00682  -0.1124   0.3217   1.0000
   5.750   1.1265   0.01499   0.00717  -0.1117   0.3011   1.0000
   6.000   1.1493   0.01545   0.00757  -0.1110   0.2832   1.0000
   6.250   1.1719   0.01592   0.00798  -0.1102   0.2647   1.0000
   6.500   1.1937   0.01644   0.00843  -0.1094   0.2448   1.0000
   6.750   1.2148   0.01699   0.00891  -0.1084   0.2272   1.0000
   7.000   1.2359   0.01754   0.00943  -0.1075   0.2101   1.0000
   7.250   1.2560   0.01814   0.00997  -0.1064   0.1920   1.0000
   7.500   1.2752   0.01878   0.01056  -0.1052   0.1781   1.0000
   7.750   1.2941   0.01942   0.01118  -0.1040   0.1636   1.0000
   8.250   1.3259   0.02103   0.01261  -0.1007   0.1304   1.0000
   8.500   1.3402   0.02182   0.01335  -0.0989   0.1165   1.0000
   8.750   1.3545   0.02255   0.01407  -0.0970   0.1031   1.0000
   9.000   1.3678   0.02334   0.01485  -0.0950   0.0958   1.0000
   9.250   1.3807   0.02416   0.01568  -0.0931   0.0908   1.0000
   9.500   1.3952   0.02488   0.01649  -0.0914   0.0862   1.0000
   9.750   1.4077   0.02575   0.01742  -0.0895   0.0813   1.0000
  10.000   1.4200   0.02665   0.01838  -0.0877   0.0768   1.0000
  10.500   1.4407   0.02881   0.02059  -0.0842   0.0628   1.0000
  10.750   1.4482   0.03016   0.02193  -0.0824   0.0583   1.0000
  11.000   1.4580   0.03140   0.02325  -0.0808   0.0544   1.0000
  11.250   1.4663   0.03279   0.02472  -0.0794   0.0505   1.0000
  11.500   1.4738   0.03431   0.02631  -0.0779   0.0465   1.0000
  11.750   1.4840   0.03564   0.02776  -0.0768   0.0417   1.0000
  12.000   1.4903   0.03737   0.02954  -0.0756   0.0374   1.0000
  12.250   1.4959   0.03922   0.03145  -0.0745   0.0356   1.0000
  12.500   1.5005   0.04124   0.03352  -0.0735   0.0337   1.0000
  12.750   1.5041   0.04342   0.03576  -0.0726   0.0318   1.0000
  13.000   1.5079   0.04566   0.03812  -0.0718   0.0301   1.0000
  13.250   1.5110   0.04804   0.04062  -0.0712   0.0288   1.0000
  13.500   1.5131   0.05062   0.04331  -0.0708   0.0276   1.0000
  13.750   1.5139   0.05343   0.04623  -0.0705   0.0266   1.0000
  14.000   1.5136   0.05646   0.04939  -0.0704   0.0257   1.0000
  14.250   1.5146   0.05944   0.05250  -0.0704   0.0250   1.0000
  14.500   1.5177   0.06224   0.05547  -0.0705   0.0242   1.0000
  14.750   1.5200   0.06524   0.05863  -0.0708   0.0234   1.0000
  15.000   1.5213   0.06845   0.06201  -0.0713   0.0223   1.0000
  15.250   1.5219   0.07184   0.06560  -0.0719   0.0206   1.0000
  15.500   1.5210   0.07555   0.06946  -0.0727   0.0167   1.0000
  15.750   1.5067   0.08142   0.07529  -0.0745   0.0097   1.0000
  16.000   1.4930   0.08746   0.08140  -0.0766   0.0058   1.0000
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